U.S. patent application number 10/353660 was filed with the patent office on 2004-07-29 for aircraft with forward opening inlay spoilers for yaw control.
Invention is credited to Clark, Walter Dennis.
Application Number | 20040144893 10/353660 |
Document ID | / |
Family ID | 32736231 |
Filed Date | 2004-07-29 |
United States Patent
Application |
20040144893 |
Kind Code |
A1 |
Clark, Walter Dennis |
July 29, 2004 |
Aircraft with forward opening inlay spoilers for yaw control
Abstract
An aircraft comprises first and second wings positioned on
opposite sides of a longitudinal axis, a first forward opening
control surface attached to an upper surface of the first wing, and
a second forward opening control surface attached to an upper
surface of the second wing, wherein each of the first and second
hinges is canted with respect to a direction perpendicular to a
longitudinal axis of the aircraft. A method of providing yaw
control of an aircraft is also provided. The method comprises the
steps of providing a first forward opening, canted spoiler in a top
surface of a first wing of the aircraft, providing a second forward
opening, canted spoiler in a top surface of a second wing of the
aircraft, and operating the first and second spoilers
differentially to create a yaw moment. The creation of yaw moments
without any down force has application in sweptback wings where the
tips are behind the center of gravity of the aircraft. The
advantage is in reducing radar cross section over traditional
(forward hinged, rearward opening) spoilers where there must be a
spoiler on the bottom side to counter the down force created by the
top spoiler.
Inventors: |
Clark, Walter Dennis;
(Fullerton, CA) |
Correspondence
Address: |
Robert P. Lenart
Pietragallo, Bosick & Gordon
One Oxford Centre, 38th Floor
301 Grant Street
Pittsburgh
PA
15219
US
|
Family ID: |
32736231 |
Appl. No.: |
10/353660 |
Filed: |
January 29, 2003 |
Current U.S.
Class: |
244/36 |
Current CPC
Class: |
B64C 2039/105 20130101;
B64C 2001/0045 20130101; B64C 9/32 20130101; B64D 7/00 20130101;
B64C 9/323 20130101; B64C 39/10 20130101; Y02T 50/10 20130101; Y02T
50/30 20130101; B64C 1/0009 20130101; Y02T 50/40 20130101; B64C
5/08 20130101 |
Class at
Publication: |
244/036 |
International
Class: |
B64C 001/00; B64C
003/00 |
Claims
What is claimed is:
1. An aircraft comprising: first and second of wings positioned on
opposite sides of a longitudinal axis; the first forward opening
control surface being attached by a first hinge to an upper surface
of the first wing; and the second forward opening control surface
being attached by a second hinge to an upper surface of the second
wing; wherein each of the first and second hinges is canted with
respect to a direction perpendicular to the longitudinal axis.
2. The aircraft of claim 1, wherein: each of the first and second
hinges is canted at an angle of between 20 and 50 degrees with
respect to a line perpendicular to the longitudinal axis.
3. The aircraft of claim 1, wherein: the first and second forward
opening control surfaces can be raised to various amounts of
opening to generate various amounts of drag, with the drag being
displaced laterally from the centerline to produce various amounts
of yaw moment.
4. The aircraft of claim 1, wherein: the first forward opening
control surface has a substantially rectangular shape, with the aft
edge of the first forward opening control surface being connected
to the first wing by the first hinge; and the second forward
opening control surface has a substantially rectangular shape, with
the aft edge of the second forward opening control surface being
connected to the second wing by the second hinge.
5. The aircraft of claim 1, wherein the first forward opening
control surface, and the second forward opening control surface
each comprise an inlay spoiler for controlling yaw without the
introduction of any up or down force.
6. An aircraft, comprising: an integrated fuselage/wing structure
generally defining the aircraft; a first forward opening control
surface integrally formed with an upper surface of the integrated
fuselage/wing; and a second forward opening control surface
integrally formed with the upper surface of the integrated
fuselage/wing; wherein the first and second control surfaces are
canted with respect to air flow during flight of the aircraft.
7. An aircraft according to claim 6, wherein the integrated
fuselage/wing structure comprises: first and second wings
positioned on opposite sides of a longitudinal axis with each of
the wings including a substantially straight swept-back leading
edge, a lower surface extending aft from the leading edge, and an
upper surface extending aft from the leading edge; the first
forward opening control surface being attached by a first hinge to
the upper surface of the first wing; and the second forward opening
control surface being attached by a second hinge to the upper
surface of the second wing; wherein each of the first and second
hinges is canted with respect to a direction perpendicular to the
longitudinal axis.
8. The aircraft of claim 7, wherein: each of the first and second
hinges is canted at an angle of between 20 and 50 degrees with
respect to a line perpendicular to the longitudinal axis.
9. The aircraft of claim 7, wherein: the first and second forward
opening control surfaces can be raised to various amounts of
opening to generate various amounts of drag, with the drag being
displaced laterally from the centerline to produce various amounts
of yaw moment.
10. The aircraft of claim 6, wherein: the first forward opening
control surface has a substantially rectangular shape, with the aft
edge of the first forward opening control surface being connected
to the first wing by a first hinge; and the second forward opening
control surface has a substantially rectangular shape, with the aft
edge of the second forward opening control surface being connected
to the second wing by a second hinge.
11. The aircraft of claim 6, wherein the first forward opening
control surface, and the second forward opening control surface
each comprise an inlay spoiler for controlling yaw without the
introduction of any up or down force.
12. A method of providing yaw control of an aircraft, the method
comprising the steps of: providing a first forward opening, canted
spoiler in a top surface of a first wing of the aircraft; providing
a second forward opening, canted spoiler in a top surface of a
second wing of the aircraft; and operating the first and second
spoilers differentially to create a yaw moment.
13. The method of claim 12, wherein: the first forward opening
control surface is attached by a first hinge to the upper surface
of the first wing; and the second forward opening control surface
is attached by a second hinge to the upper surface of the second
wing; wherein each of the first and second hinges is canted with
respect to a direction perpendicular to a longitudinal axis of the
aircraft.
14. The method of claim 13, wherein: each of the first and second
hinges is canted at an angle of between 20 and 50 degrees with
respect to a line perpendicular to the longitudinal axis.
15. The method of claim 12, wherein: the first and second forward
opening control surfaces can be raised to various amounts of
opening to generate various amounts of drag, with the drag being
displaced laterally from the centerline to produce various amounts
of yaw moment.
16. The method of claim 12, wherein: the first forward opening
control surface has a substantially rectangular shape, with the aft
edge of the first forward opening control surface being connected
to the first wing by a first hinge; and the second forward opening
control surface has a substantially rectangular shape, with the aft
edge of the second forward opening control surface being connected
to the second wing by a second hinge.
17. The method of claim 12, wherein the first forward opening
control surface, and the second forward opening control surface
each comprise an inlay spoiler for controlling yaw without the
introduction of any up or down force.
Description
FIELD OF THE INVENTION
[0001] The invention relates generally to aircraft, and more
specifically, to systems and methods for control of an
aircraft.
BACKGROUND INFORMATION
[0002] Aircraft purposefully built to avoid radar detection are
characterized by shapes with as few different angles as possible.
This results in edges which are parallel to each other even if on
opposite sides of the aircraft. It is also desirable to have a
fuselage that is blended into the wing where any shapes of small
radius can be placed on the upper side, unseen by ground radar.
Because of this smooth integration, these aircraft are sometimes
referred as "flying wings." An example of a flying wing aircraft is
the B-2 bomber. An aircraft of low radar cross section is devoid of
any unnecessary protuberances such as a vertical stabilizer, having
its function replaced by control surfaces that increase the drag on
one wing or the other only when needed and otherwise lie against
the wing to become part of the wing.
[0003] The advantages of all-wing, tailless aircraft are known. For
example, tailless aircraft provide enhanced stealthy operating
characteristics due to their inherent low-observable configuration.
Moreover, all-wing aircraft provide other benefits such as improved
efficiency due to reduced weight and drag and, accordingly, are
well suited for use in a wide variety of applications such as in
autonomous (unmanned) aircraft where the bulge for a pilot to look
out doesn't have to be accommodated.
[0004] A significant disadvantage of the tailless aircraft
configuration lies in the absence of an aircraft rudder normally
incorporated within the vertical tail section. The rudder is
provided in conventional aircraft to provide a side to side or yaw
moment to the aircraft in flight. Therefore, without a rudder,
other means must be provided to impart yaw moment to the tailless
aircraft. Traditionally, tailless aircraft use spoilers in the
outboard part of the wing. Either the left side or the right side
can be made to open to control the lateral direction of flight.
These spoilers are either made a part of the existing elevons,
elevators or ailerons in the form of split flaps or they are
mounted ahead of these surfaces in the form of inlay-spoilers.
Elevons, ailerons and elevators on all wing aircraft have a minimal
contribution to radar cross section. The spoiler is the largest
detractor of stealth because it forms acute angles with the surface
it emerges from. Traditional inlay spoilers can be low in cross
section if they are only opened on the top side. The wing itself
masks the view from below. But a topside only spoiler of
conventional design produces a down force and, if the spoiler is
near the tip of a sweptback wing, the resulting force will pitch
the airplane upward.
[0005] As such, based upon the foregoing, there exists a need in
the art for an improved method and device, which improves aircraft
yaw control characteristics without substantially interfering with
the aircraft aerodynamic and radar detectability
characteristics.
SUMMARY OF THE INVENTION
[0006] This invention provides an aircraft comprising first and
second wings positioned on opposite sides of a longitudinal axis. A
first forward opening control surface is attached by a first hinge
to an upper surface of the first wing, and a second forward opening
control surface is attached by a second hinge to an upper surface
of the second wing, wherein each of the first and second hinges is
canted with respect to a direction perpendicular to the
longitudinal axis. The opening of these forward opening surfaces
introduces drag on one wing or the other. It is the drag some
distance laterally from the centerline that produces a yaw
force.
[0007] The hinges can be canted, at an angle of between 20 and 50
degrees with respect to a line perpendicular to the longitudinal
axis.
[0008] The first and second forward opening control surfaces can be
canted to throw the air outward or inward so that the air can
escape sideways instead of building up in front of the spoiler. If
the air was allowed to build up in front, the surface would produce
a down force just like the traditional hinge-in-front spoilers.
[0009] The first forward opening control surfaces can have a
substantially rectangular shape, with an aft edge of each control
surface being connected to one of the wings by a hinge.
[0010] The forward opening control surfaces produce drag and a side
force to control yaw without the introduction of any up or down
force.
[0011] This invention can be applied to an integrated fuselage/wing
structure generally defining the aircraft, wherein the first and
second wings are positioned on opposite sides of the longitudinal
axis with each of the wings including a substantially straight
swept-back leading edge, a lower surface extending aft from the
leading edge, and an upper surface extending aft from the leading
edge, and the control surfaces can be attached by hinges that are
canted with respect to the lateral axis, a direction parallel to
the horizon but perpendicular to the longitudinal axis.
[0012] The aircraft can further include additional control surfaces
on the upper surface of the integrated fuselage/wing.
[0013] The invention also encompasses a method of providing yaw
control of an aircraft, the method comprising the steps of
providing a first forward opening, canted spoiler in a top surface
of a first wing of the aircraft, providing a second forward
opening, canted spoiler in a top surface of a second wing of the
aircraft, and operating the first and second spoilers
differentially to create a yaw moment.
BRIEF DESCRIPTION OF THE DRAWINGS
[0014] FIG. 1 is a schematic representation of a perspective view
of a swept back aircraft that can be constructed in accordance with
this invention.
[0015] FIG. 2 is a schematic representation of a top plan view of
the aircraft of FIG. 1, showing inlaid spoilers.
[0016] FIG. 3 is a schematic representation of a top plan view of
an aircraft showing yaw control spoilers.
[0017] FIG. 4 is a schematic representation of a side view of a
portion of a wing and a vertical spoiler.
[0018] FIG. 5 is a schematic representation of a side view of a
portion of a wing and a forward opening spoiler.
DETAILED DESCRIPTION OF THE INVENTION
[0019] In accordance with an aspect of the invention, a flying wing
tailless aircraft comprises an integrated fuselage/wing that
generally defines the aircraft and control surfaces integrally
formed therewith. FIG. 1 is a schematic representation of a
perspective view of a swept back aircraft 10 that can be
constructed in accordance with this invention. The aircraft 10 has
a longitudinal axis 12 and is provided with a central fuselage 14
positioned along the longitudinal axis. A pair of opposing swept
back wings 16, 18 extend laterally and in an aftward direction from
the fuselage 14. The wings 16, 18 have an outer contour which
blends smoothly and continuously with that of the fuselage 14. In
this respect, the fuselage 14 is completely integrated with the
wings 16, 18. This smooth integration is contemplated to give the
entire aircraft 10 the appearance and functionality of being a
single wing. Thus, the integrated fuselage/wing configuration
generally defines the aircraft 10. As such, the aircraft 10 may be
characterized by having a relatively low aspect ratio and a
generally triangular or delta-shaped planform.
[0020] The aircraft 10 is provided with an upper surface and a
lower surface. The upper and the lower surfaces encompass both the
fuselage 14 and the wings 16, 18. FIG. 1 shows the lower surface
20. In addition, the wings 16, 18 include leading edges 22, 24,
respectively. The leading edges 22, 24 are configured to, for
example, form a continuous straight contour. Such a straight
contour is desirable in light of radar signature mitigation
considerations, i.e., forming a low-observable, delta-shaped
aircraft. The leading edges 22, 24 of the wings 16, 18 along with
the upper surface of the aircraft 10 generally define the
aerodynamic lifting surface of the aircraft 10. As such, the
aerodynamic lifting surface is generally disposed about the
fuselage 14 and the wings 16, 18. The wings 16, 18 also include
trailing edges 26, 28, respectively.
[0021] FIG. 2 is a schematic representation of a top plan view of
the aircraft of FIG. 1. As seen in FIG. 2, the aircraft 10 also
includes control surfaces 30, 32, 34, 36, 38 and 40 that are
integrally formed with the upper surface 42 of the fuselage/wing
configuration. Specifically, the control surfaces may include, for
example, elevons, ailerons, elevators, rudders, trim tabs, or
similar components that are well known in the art.
[0022] In accordance with this invention, some control surfaces can
be positioned in the top surface of the aircraft so as to prevent
them from being seen by ground radar. The particular control
surface which should be only on the top are those that open up so
as to create drag. The other surfaces, the elevator and ailerons,
can be hinged to move up and down with little sacrifice in radar
cross section. The topside only control surfaces are called inlay
spoilers and can be operated to control the yaw of the aircraft. A
conventional inlay-spoiler opens up like a hatch door with a hinge
on the upwind side. It creates drag but also creates a force into
the wing. In this invention, the yaw control inlay-spoiler is
hinged in the back. In one embodiment, at least some of the control
surfaces can be this hinged-in-the-back inlaid spoiler type that
can be operated between open and retracted positions. When in the
retracted position, the surfaces of the spoilers conform to the
surface of the wings.
[0023] By operating a pair of conventional inlays 30, 32 (hinged in
the front) in the front of the aircraft, a down-moment can be
produced. A pair of conventional inlays 34, 36 in the back can
provide an up-moment. Thus inlays 30, 32, 34 and 36 can be operated
in pairs to provide pitch control. Since inlay spoilers are very
high drag devices, trimming in pitch can be done with fuel
shifting. Roll control can be achieved by operating the same four
inlays in pairs laterally. That is, pairs 30 and 34, or 32 and 36
can be operated to provide roll control. The inlays 38 and 40 near
the wing tips 44, 46 provide yaw control.
[0024] Inlays 38 and 40 are forward opening inlaid-spoilers.
Forward-opening inlaid- spoilers for yaw control can provide pure
yaw and are free of any pitch or roll moment if their hinges are
canted with respect to air flow. If the air were allowed to build
up in front, the surface would produce a down force just like the
conventional hinge-in-front spoilers.
[0025] This invention permits a reduction in the aircraft radar
cross-section by eliminating the need for bottom-side spoilers so
that surface discontinuities in the bottom of the aircraft can be
minimized. The particular problem with spoilers with regard to
radar signature is that in opening they form an acute angle with
the surface they rise out of. This creates a retro-reflecting
structure for radar to bounce off of.
[0026] FIG. 3 is a schematic representation of a top plan view of
an aircraft 50 showing yaw control spoilers 52 and 54. The
spoilers' are hinged along edges 56 and 58 so that they open in a
forward direction. The spoilers are canted with respect to the
longitudinal axis of the aircraft at angles .theta..sub.1 and
.theta..sub.2. Angles .theta..sub.1 and .theta..sub.2 can be the
same angle. Arrows 60, 62, 64 and 66 show the direction of air flow
in the vicinity of the spoilers. Since the spoilers are canted
outward, air is directed toward the wing tips 68 and 70.
[0027] By adjusting the cant angle (the azimuth position of the
inlay) the up or down force can be brought to zero for pure yaw
control. This is important in swept wings because the tips are so
far aft. Even vertical spoilers with all their mechanical
complexity produce a down force. FIG. 4 is a schematic
representation of a side view of a portion of a wing 72 and a
vertical spoiler 74 positioned in a top surface 76 of the wing.
Arrows 78, 80, 82 and 84 illustrate air flow in the vicinity of the
spoiler 74 showing how air is deflected upward with a consequent
down force.
[0028] FIG. 5 is a schematic representation of a side view of a
portion of a wing 86 and a forward opening spoiler 88 positioned in
a top surface 90 of the wing. Arrows 92, 94 and 96 illustrate air
flow in the vicinity of the spoiler 88.
[0029] FIG. 4 shows that a vertical spoiler 74 causes a net change
in momentum upward, whereas with a canted and tilted surface as
shown in FIG. 5, much of the air is withdrawn without going up.
This is shown in FIG. 5 where the arrow 94 shows the air escaping
horizontally. Drag is still created but by canting the surface the
airflow is kept from damming up in front of the spoiler, which
would force the air up and over like a vertical spoiler. The side
deflection can be outward or inward. By choosing outward
deflection, the air thrown to the side imparts an inward force that
produces a moment, which is in the same direction as the moment due
to drag. By adjusting the cant angle, the down force produced by
the forward opening spoiler can be balanced against the up force of
the air piling up in front of the spoiler.
[0030] This invention is particularly applicable to swept back
flying wing aircraft because there is no force down into the wing.
Ordinary inlay-spoilers (hinged in the front) will impart a down
force which will pitch the aircraft up. Since this invention
provides a yaw moment without an up or down force it can be used
for wings where the tips are behind the center of gravity.
[0031] To demonstrate, in a model, the pure yaw behavior of the
forward opening spoiler, the variable dihedral effect of the
sweepback must be overcome. Otherwise, the yaw will produce a roll
which would mask the unwanted roll produced by any down force. The
effect of the sweepback can be overcome by flying the model with
the weight off the wings. A model was built and then test flown at
zero lift, that is, in a ballistic trajectory. That allowed the yaw
to occur without affecting roll. If the model rolled in zero lift,
it must be due to the unwanted up or down force.
[0032] To perform that test, a remote control catapult model was
made with a single topside-only forward opening spoiler. This was
added to an existing model that was equipped with normal control
surfaces. The normal controls were used to recover the airplane
after the ballistic flight to land it safely. The trajectory of the
airplane upon launch can be judged by the eye to be ballistic. The
transmitter's pitch trim was adjusted until the familiar arc was
achieved. Just before hitting the ground, the control stick was
pulled back for a gentle landing.
[0033] A shroud was provided in front of the inlay to keep the
leading edge of the new spoiler flush with the skin. The shroud and
the spoiler could be rotated in azimuth or even repositioned on the
wing for different test flights. In practice, the surfaces would
not necessarily share the same place on the wing.
[0034] After several ballistic launches and subsequent recovery
maneuvers, a flight was made where near the top of the trajectory,
the forward-opening spoiler was popped open. Success could be
measured by seeing the surface open up without the airplane
rolling, or pitching. A canted angle of about 50 degrees produced
pure yaw.
[0035] In this invention, the inlay-spoilers on the top surface of
the aircraft are not matched by anything on the bottom.
Inlay-spoilers and topside control surfaces have been used
previously, but they have all been hinged in the front or they rose
vertically. When these conventional inlays are installed on the
topside of swept or delta wings, they must be balanced by
inlay-spoilers on the bottom. An unbalanced surface in the back
will affect both pitch and roll. But with this invention, the yaw
control spoilers are self-balancing. The bottom skin need not have
any control surface on it and is thus more easily rendered low in
radar cross section.
[0036] This invention provides a wing mounted yaw control device.
The wing mounted yaw control device includes spoilers hingedly
mounted on a top surface and canted with respect to the
longitudinal axis of the aircraft. A deployment mechanism can be
provided to effect deployment of the spoilers. During operation,
the spoilers can be selectively deployed in order to impart an
unbalanced drag force on one wing, thereby imparting the desired
yaw moment to an aircraft in flight.
[0037] The creation of yaw moments, without any down force, has
application in sweptback wings where the tips are behind the center
of gravity of the aircraft. This invention provides the advantage
of reducing radar cross section over traditional (forward hinged,
rearward opening) spoilers where there must be a spoiler on the
bottom side to counter the down force created by the top spoiler.
However, this invention can be used on any wing planform.
[0038] Using this invention on a swept wing takes advantage of the
canted hinge-line. The discovered phenomenon is that a forward
opening spoiler produces drag without a change in the pitch moment
as long as the hinge-line is canted away from being perpendicular
with the airflow. The cant angle can be such as to dump the air
either away from the centerline or toward it. When the surface is
raised, this cant angle produces a lateral force, which is also,
either toward or away from the centerline. It is important to
carefully choose whether this force is toward or away based on the
sweep angle. In a swept back wing, the control surface is aft of
the center of gravity, and if the hinge-line is canted so the side
force is inward, a moment is produced that is in the same sense as
the moment produced by the drag. With the same line of reasoning,
if the wing is swept forward there is an advantage in canting the
hinge-line of the surface to dump the air inwardly. If the wing is
straight the hinge line must still be canted away, but there is no
advantage to dumping the air in either direction. Only the drag
component is useful.
[0039] The invention also encompasses a method of providing yaw
control of an aircraft, the method comprising the steps of
providing a first forward opening, canted spoiler in a top surface
of a first wing of the aircraft, providing a second forward
opening, canted spoiler in a top surface of a second wing of the
aircraft, and operating the first and second spoilers
differentially to create a yaw moment.
[0040] While particular embodiments of this invention have been
described above for purposes of illustration, it will be evident to
those skilled in the art that numerous variations of the details of
the present invention may be made without departing from the
invention as defined in the appended claims.
* * * * *